E61 (5.64%) (e61-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 200,000 Max Cl/Cd: 112.53 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e61-il-200000.txt Download as CSV file: xf-e61-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E61 (5.64%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.250 -0.2615 0.10287 0.09979 -0.0437 0.9726 0.0193
-6.000 -0.2533 0.09717 0.09409 -0.0416 0.9703 0.0202
-5.750 -0.2431 0.09370 0.09063 -0.0420 0.9644 0.0210
-5.500 -0.2205 0.09002 0.08693 -0.0467 0.9607 0.0218
-5.250 -0.2069 0.08699 0.08388 -0.0494 0.9537 0.0226
-5.000 -0.1817 0.08312 0.08000 -0.0551 0.9493 0.0239
-4.750 -0.1619 0.07977 0.07664 -0.0595 0.9430 0.0250
-4.500 -0.1332 0.07592 0.07277 -0.0662 0.9381 0.0264
-4.250 -0.0780 0.07133 0.06810 -0.0810 0.9355 0.0290
-4.000 -0.0274 0.06770 0.06437 -0.0944 0.9281 0.0298
-3.750 0.0019 0.06145 0.05810 -0.1006 0.9254 0.0309
-3.500 0.0221 0.05840 0.05506 -0.1011 0.9233 0.0335
-3.250 0.0552 0.05517 0.05177 -0.1068 0.9179 0.0366
-3.000 0.1365 0.04862 0.04497 -0.1259 0.9165 0.0443
-2.750 0.1689 0.04599 0.04231 -0.1293 0.9136 0.0496
-2.500 0.2511 0.04014 0.03611 -0.1460 0.9137 0.0584
-2.250 0.3197 0.03619 0.03174 -0.1575 0.9134 0.0711
-2.000 0.3583 0.03379 0.02936 -0.1613 0.9120 0.0773
-1.750 0.4209 0.03080 0.02589 -0.1703 0.9118 0.0996
-1.500 0.4641 0.02895 0.02401 -0.1745 0.9107 0.1188
-1.250 0.5432 0.02358 0.01733 -0.1836 0.9126 0.0519
-1.000 0.5909 0.02185 0.01501 -0.1870 0.9117 0.0434
-0.750 0.6334 0.02086 0.01383 -0.1897 0.9104 0.0423
-0.500 0.6775 0.01958 0.01246 -0.1929 0.9095 0.0434
-0.250 0.7042 0.01919 0.01211 -0.1930 0.9021 0.0503
0.000 0.7454 0.01856 0.01143 -0.1955 0.8996 0.0582
0.250 0.7921 0.01738 0.01107 -0.1998 0.8984 0.3490
0.500 0.8245 0.01592 0.01071 -0.2001 0.8967 1.0000
0.750 0.8502 0.01598 0.01065 -0.1996 0.8886 1.0000
1.000 0.8895 0.01560 0.01016 -0.2016 0.8858 1.0000
1.250 0.9313 0.01510 0.00958 -0.2041 0.8840 1.0000
1.500 0.9602 0.01499 0.00944 -0.2041 0.8768 1.0000
1.750 1.0001 0.01451 0.00892 -0.2061 0.8732 1.0000
2.000 1.0453 0.01391 0.00831 -0.2092 0.8707 1.0000
2.250 1.0764 0.01372 0.00812 -0.2096 0.8627 1.0000
2.500 1.1207 0.01319 0.00765 -0.2125 0.8580 1.0000
2.750 1.1539 0.01297 0.00745 -0.2133 0.8492 1.0000
3.000 1.1976 0.01250 0.00700 -0.2161 0.8426 1.0000
3.250 1.2278 0.01239 0.00693 -0.2163 0.8309 1.0000
3.500 1.2593 0.01226 0.00689 -0.2166 0.8181 1.0000
3.750 1.2904 0.01218 0.00685 -0.2169 0.8042 1.0000
4.000 1.3210 0.01213 0.00683 -0.2171 0.7887 1.0000
4.250 1.3467 0.01219 0.00693 -0.2162 0.7699 1.0000
4.500 1.3730 0.01226 0.00707 -0.2154 0.7488 1.0000
4.750 1.3965 0.01241 0.00725 -0.2141 0.7249 1.0000
5.000 1.4189 0.01261 0.00746 -0.2126 0.6978 1.0000
5.250 1.4398 0.01288 0.00769 -0.2107 0.6642 1.0000
5.500 1.4528 0.01337 0.00793 -0.2071 0.6007 1.0000
5.750 1.4563 0.01446 0.00841 -0.2018 0.5011 1.0000
6.000 1.4582 0.01583 0.00921 -0.1966 0.4114 1.0000
6.250 1.4619 0.01718 0.01018 -0.1921 0.3342 1.0000
6.500 1.4635 0.01877 0.01124 -0.1874 0.2510 1.0000
6.750 1.4679 0.02042 0.01242 -0.1835 0.1733 1.0000
7.000 1.4671 0.02280 0.01407 -0.1789 0.0751 1.0000
7.250 1.4666 0.02544 0.01632 -0.1739 0.0254 1.0000
7.500 1.4733 0.02731 0.01830 -0.1702 0.0190 1.0000
7.750 1.4845 0.02869 0.01984 -0.1673 0.0170 1.0000
8.000 1.4927 0.03037 0.02170 -0.1640 0.0158 1.0000
8.250 1.5000 0.03225 0.02373 -0.1607 0.0149 1.0000
8.500 1.5077 0.03430 0.02592 -0.1575 0.0143 1.0000
8.750 1.5175 0.03655 0.02836 -0.1547 0.0140 1.0000
9.000 1.5320 0.03904 0.03101 -0.1526 0.0138 1.0000
9.250 1.5553 0.04196 0.03416 -0.1516 0.0139 1.0000
9.500 1.5894 0.04617 0.03880 -0.1519 0.0146 1.0000
9.750 1.6149 0.05144 0.04464 -0.1511 0.0157 1.0000
10.000 1.6222 0.05674 0.05045 -0.1482 0.0168 1.0000
10.250 1.6182 0.06210 0.05623 -0.1443 0.0177 1.0000
10.500 1.6158 0.06957 0.06457 -0.1387 0.0242 1.0000
10.750 1.4781 0.06956 0.06470 -0.1201 0.0177 1.0000
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Polar data table (+)
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